Sovereign 680 - Limitations and Memory Items

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mhumberd
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63472
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Sovereign 680 - Limitations and Memory Items
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2011-02-01 16:48:58
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Sovereign Limitations Memory Items
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Sovereign 680 - Limitations and Memory Items
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  1. Environmental System Smoke or Odor
    1. Oxygen Masks/Googles........Don and EMER
  2. Electrical System Smoke Or Fire
    1. Oxygen Masks/Googles........Don and EMER
  3. Smoke Removal
    1. Oxygen Masks/Googles........Don and EMER
  4. Hydraulic Wheel Brake Failure
    • 1. Brake Pedals.........Remove Feet
    • 2. EMERGENCY BRAKE Handle.....Pull and Hold Until Stopped
  5. Aileron Trim Runaway
    1. AP/TRIM/NWS DISC Button......Push and Hold
  6. Primary Pitch Trim Runaway
    1. AP/TRIM/NWS DISC Button......Push and Hold
  7. Secondary Pitch Trim Runaway
    1. SECONDARY TRIM Button.........OFF
  8. Jammed Pitch Or Roll Control System
    • 1. Stabilizer Trim Switch........Actuate to establish desired pitch attitude
    • 2. Control Wheel.............Relax Pressure
    • 3. PITCH/ROLL RECONNECT Handle......Pull until Latched
    • 4. Operative Flight Control Wheel.........Identify, Recover Airplane Attitude

    *Warning*

    Stabilizer trim must e used to rotate to a takeoff attitude and/or arrest pitch rate if jam occurs during takeoff, landing, or other critical phase of flight.
  9. Rudder Trim Runaway
    1. AP/TRIM/NWS DISC Button......Push and Hold
  10. Nosewheel Steering Malfunction
    1. AP/TRIM/NWS DISC Button......Push and Hold
  11. Inadvertent Stall (Buffet/Roll-off)
    • 1. AP/TRIM/NWS DISC Button......Push
    • 2. Pitch Attitude......Reduce
    • 3. Roll Attitude........Wings Level
    • 4. Throttles...............TO Detent
  12. WINDSHR

    This message is displayed in the right portion of the PFD ADIS when a TAWS windshear warning alert is active, indicating an increasing tailwind or severe downdraft condition. An aural "WINDSHEAR WINDSHEAR WINDSHEAR" warning accompanies this message. Windshear escape flight guidance is not provided.
    • 1. Throttles.................................TO Detent
    • 2. Pitch Attitude..........................Go-Around Attitude (7.5 Degrees)
    • 3. SPEEDBRAKE Handle...........0%
  13. APU Fire (Red CAS message)
    1. APU Fire Button..............Push
  14. Battery O'Temp L and/or R (Red CAS Message)
    1. BATT Button (affected Side).............OFF
  15. Cabin Altitude (Red CAS Message)
    • 1. Oxygen Masks...................Don and 100%
    • 2. Left and Right MIC SEL Buttons........MASK
    • 3. Emergency Descent..........................As Required
  16. DPLY (Red EICAS Indication) and EMER STOW (Switch Flashing)
    • 1. T/R EMER STOW Button (Flashing Button).....Push
    • 2. Throttle (Affected engine)......................IDLE
    • 3. Airspeed..........................Reduce to 150 KIAS Maximum
  17. Emergency Descent (Red CAS Message)
    1. Initiate Maximum Rate of descent to a safe altitude
  18. Engine Fire L and/or R (Red CAS Message)

    Takeoff Above V1 or in flight at a safe Altitude at or above 400 ft AGL and conditions permit
    • 1. Throttle (affected engine)...................IDLE
    • 2. ANTI-ICE WING/STAB XFLOW Button (if bleed air anti-ice systems are on).................XFLOW

    • If ENG FIRE Light Still Illuminated After 15 Seconds
    • 3. Illuminated ENG FIRE Button..............Push
    • 4. Either Illuminated BOTTLE ARMED Button.......Push
  19. Engine Fire L and/or R (Red CAS Message)
    Takeoff below V1 or on the Ground
    1. Takeoff........................Abort
  20. No Takeoff (Red CAS Message)
    Speed Below V1 - Takeoff Rejected
    1. Takeoff.......................Abort
  21. No Takeoff (Red CAS Message)Speed Below V1 - Takeoff Continued
    1. Climb to a Safe Altitude
  22. Engine Failure or other Emergency During Takeoff
    Speed Below V1
    1. Takeoff.......................Abort
  23. Engine Failure or other Emergency During Takeoff
    Speed at or above V1
    • 1. Climb to Safe Altitude
    • 2. ANTI-ICE WING/STAB XFLOW Button (if bleed air anti-ice systems are on).............................XFLOW
  24. Engine Failure During Final Approach
    • 1. Flaps............................15 Degrees
    • 2. Airspeed.......................Vapp
  25. Dual Engine Flameout - Cruise
    Crew Oxygen Masks (If Required).................DON
  26. Dual Engine Flameout - Low Altitude
    • 1. Fuel.................................................Check Tanks/Quantity
    • 2. FUEL BOOST Buttons (Both)...............ON
    • 3. Throttles.................................................CUTOFF
  27. Certification Status
    This Citation Sovereign is certified in accordance with 14 CFR Part_____ and JAR-_____
    • Certification Status
    • This Citation Sovereign is certified in accordance with 14 CFR Part 25 and JAR-25
  28. Certification Status
    Maximum Design Ramp Weight.......................?
    Maximum Design Takeoff Weight....................?
    Maximum Design Landing Weight....................?
    Maximum Design Zero Fuel Weight.................?
    Maximum Tailcone Baggage Weight.................?
    Maximum Certified Landing Weight..................?
    • Certification Status
    • Maximum Design Ramp Weight.......................30,550 Pounds
    • Maximum Design Takeoff Weight....................30,300 Pounds
    • Maximum Design Landing Weight..................27,100 Pounds
    • Maximum Design Zero Fuel Weight.................20,800 Pounds
    • Maximum Tailcone Baggage Weight.................1,000 Pounds
    • Maximum Certified Landing Weight..................27,100 Pounds
  29. Powerplant Limitations
    Engine Type.........Pratt and Whitney Canada Inc. ______ Turbofan (producing ______lbs. thrust at sea level up to 30 C)

    Attempting an engine start is prohibited with a tailwind component greater than _____knots.
    • Powerplant Limitations
    • Engine Type.........Pratt and Whitney Canada Inc. PW306C Turbofan (producing 5,770 lbs. thrust at sea level up to 30 C)

    Attempting an engine start is prohibited with a tailwind component greater than 10 knots.
  30. FADEC
    (Full Authority Digital Engine Computers)

    Dispatch with an engine FADEC ______ inoperative is prohibited.
    Both air data systems must be _______ for dispatch.
    Maximum oil consumption is 1 quart per ____-hour period.
    • FADEC
    • (Full Authority Digital Engine Computers)

    • Dispatch with an engine FADEC channel inoperative is prohibited.
    • Both air data systems must be operational for dispatch.
    • Maximum oil consumption is 1 quart per 8-hour period.
  31. Engine Operating Limits

    Starting ITT Limit..............................?
    Max Observed ITT Limit (TO Detent)................?
    Takeoff ITT Time Limit (TO Detent): .............____minutes (_____for single engine operation)
    Max Continuous ITT Limit (MCT Detent)...............?
    Engine Operating Limits

    • Starting ITT Limit.............................................950 C
    • Max Observed ITT Limit (TO Detent)..............920 C
    • Takeoff ITT Time Limit (TO Detent): .............5 minutes (10 for single engine operation)
    • Max Continuous ITT Limit (MCT Detent)...............920 C
  32. Engine Operating Limits

    N1 Limit................................?
    Transient N1 Limit (20 Seconds)..................?
    N2 Limit...........................................?
    Transient N2 Limit (20 Seconds)..................?
    Engine Operating Limits

    • N1 Limit................................................105%
    • Transient N1 Limit (20 Seconds)............106%
    • N2 Limit.................................................105%
    • Transient N2 Limit (20 Seconds).............106%
  33. Engine Operating Limits

    The total time during which takeoff thrust may be used is limited to ___ minutes per flight. This time may be extended to _____ minutes for one engine inoperative operation.
    Oil pressure less than ___PSI but greater than or equal to _____ PSI is acceptable when the throttles are set to less than CRU detent.
    After initiation of the start cycle, oil pressure should indicate an increase within ____ seconds of engine light-up indicated by a rise in N2 and ITT.
    Engine Operating Limits

    • The total time during which takeoff thrust may be used is limited to 5 minutes per flight. This time may be extended to 10 minutes for one engine inoperative operation.
    • Oil pressure less than 36 PSI but greater than or equal to 20 PSI is acceptable when the throttles are set to less than CRU detent.
    • After initiation of the start cycle, oil pressure should indicate an increase within 20 seconds of engine light-up indicated by a rise in N2 and ITT.
  34. Start Cycle Limitations

    Engine Starter Limitation: The rest periods between engine starts is ____ minutes after the first start attempt, ____ minutes after the second, and ____ minutes after the third.

    APU Starter Limitation: ____APU start cycles per ____ minutes. ____ cycles with a ___-second rest period between cycles is permitted.
    Start Cycle Limitations

    Engine Starter Limitation: The rest periods between engine starts is 2 minutes after the first start attempt, 5 minutes after the second, and 30 minutes after the third.

    APU Starter Limitation: 3 APU start cycles per 30 minutes. 3 cycles with a 90-second rest period between cycles is permitted.
  35. Battery Limitations

    Battery Start Limitation...................____ engine starts per hour

    Engine Start Source Count Against Battery
    Battery Start..................................................?
    GPU (greater than 1,000 amps) .....................?
    GPU (less than 1,000 amps)..........................?
    Cross-Generator.......................................... ?
    APU-Battery Start........................................?
    APU Start......................................................?
    Battery Limitations

    Battery Start Limitation...................3 engine starts per hour

    • Engine Start Source Count Against Battery
    • Battery Start..................................................1
    • GPU (greater than 1,000 amps) ....................1/3
    • GPU (less than 1,000 amps)..........................1
    • Cross-Generator.......................................... 1/3
    • APU-Battery Start........................................1/3
    • APU Start.....................................................1/3
  36. Electrical Power Systems

    Status Engine Gen Limit APU Gen Limit

    Ground.................?..................................?
    Air........................?..................................?
    > 35,000 feet........?..................................?
    Electrical Power SystemS

    Status Engine Gen Limit APU Gen Limit

    • Ground..........300 Amps.......................275 Amps
    • Air.................300 Amps.......................275 Amps
    • > 35,000 feet.....275 Amps......................N/A
  37. Electical Power Systems

    The battery temperature indicating system must be operational for all ____ and _____ operations.
    If the BATTERY O'TEMP L-R CAS message displays during ground operations, even if it subsequently clears, _____ is prohibited until after the proper maintenance procedures have been accomplished.
    For generator cooling during ground operations, the engine must be operated at idle with the generator load less than ______ prior to engine shutdown. Otherwise, a ____ minute cooling period after engine shutdown is required prior to attempting a restart.
    Electical Power Systems

    • The battery temperature indicating system must be operational for all ground and flight operations.
    • If the BATTERY O'TEMP L-R CAS message displays during ground operations,
    • even if it subsequently clears, dispatch is prohibited until after the proper maintenance procedures have been accomplished.
    • For generator cooling during ground operations, the engine must be operated at idle with the generator load less than 75 Amps for 4 minutes prior to
    • engine shutdown. Otherwise, a 35-minute cooling period after engine shutdown is required prior to attempting a restart.
  38. Auxiliary Power Unit (APU)

    The maximum altitude for APU starts is .....................?
    The maximum airspeed for APU starts is....................?
    The maximum operating altitude for the APU is...........?
    The maximum operating airspeed for the APU is _____ KIAS/ ______Mach.
    APU operation is prohibited until ______ as contained in Section III, Normal Procedures.
    _____APU start attempt is permitted after a dual generator failure.
    Auxiliary Power Unit (APU)

    • The maximum altitude for APU starts is .....................FL200
    • The maximum airspeed for APU starts is....................250 KIAS
    • The maximum operating altitude for the APU is..........FL300
    • The maximum operating airspeed for the APU is 305 KIAS/ .80 Mach.
    • APU operation is prohibited until a satisfactory APU test has been accomplished as contained in Section III, Normal Procedures.
    • One APU start attempt is permitted after a dual generator failure.
  39. Auxillary Power Unit (APU)

    Following Shutdown for any reason, an APU restart must not be attempted until _____ seconds after the RPM indicator reads 0%.

    Applying deice/anti-ice fluid of any type is prohibited when _______.
    ________ operation of the APU is prohibited.
    Auxillary Power Unit (APU)

    Following Shutdown for any reason, an APU restart must not be attempted until 30 seconds after the RPM indicator reads 0%.

    • Applying deice/anti-ice fluid of any type is prohibited when the APU is operating.
    • Unattended operation of the APU is prohibited.
  40. Auxillary Power Unit (APU)

    Operating the cockpit and cabin temperature controls in ______ is prohibited while APU MAX COOL is selected ON. A _______-second waiting period is required after selecting APU MAX COOL to OF before operating cockpit and cabin temperature controls in MANUAL.
    The APU ________ must be inspected following an automatic shutdown of the APU.
    Auxillary Power Unit (APU)

    • Operating the cockpit and cabin temperature controls in manual is prohibited while APU MAX COOL is selected ON. A 30-second waiting
    • period is required after selecting APU MAX COOL to OF before operating
    • cockpit and cabin temperature controls in MANUAL.
    • The APU compartment must be inspected following an automatic shutdown of the APU.
  41. Hydraulic Power Systems

    The use of the auxiliary hydraulic pump is prohibited when the ground operating temperature is below _____.
    The use of the auxiliary hydraulic pump is prohibited _______.
    Hydraulic Power Systems

    • The use of the auxiliary hydraulic pump is prohibited when the ground operating temperature is below -40 C.
    • The use of the auxiliary hydraulic pump is prohibited in flight.
  42. Ice and Rain Protection

    The Anti-Ice ENGINE/STAB switches must be selected ON between the temperatures of _____ when in visible moisture. Use _____ for ground operations and ____ for in flight.
    Except for the ground preflight check, maximum SAT for operation of bleed air anti-ice with the throttles above idle is ______.
    Limit the ground operation of the pitot-static hear to ____ minutes to preclude damage to the pitot tubes and angle-of-attack vanes.
    Ice and Rain Protection

    • The Anti-Ice ENGINE/STAB switches must be selected ON between the
    • temperatures of +10 C TO -35 C when in visible moisture. Use SAT for ground
    • operations and RAT for in flight.
    • Except for the ground preflight check, maximum SAT for operation of bleed air anti-ice with the throttles above idle is +20 C.
    • Limit the ground operation of the pitot-static heat to 2 minutes to preclude damage to the pitot tubes and angle-of-attack vanes.
  43. Ice and Rain Protection

    _____ must not be used to deice surfaces prior to takeoff.
    The Anti-Ice ENGINE/STAB switches must be selected ON at least ____ prior to an idle descent into an icing environment.
    Ice and Rain Protection

    • Anti-ice systems must not be used to deice surfaces prior to takeoff.
    • The Anti-Ice ENGINE/STAB switches must be selected ON at least 1 minute prior to an idle descent into an icing environment.
  44. Operations in Severe Icing Conditions

    Visual Cues
    Unusually extensive ice accumulation on the airframe and windshield in areas __________.
    Accumulation of ice on the upper surface of the wing aft of the protected area extending more than _______aft of the heated leading edge.
    Operations in Severe Icing Conditions

    • Visual Cues
    • Unusually extensive ice accumulation on the airframe and windshield in areas in areas not normally observed to collect ice.
    • Accumulation of ice on the upper surface of the wing aft of the protected area extending more than 12 to 18 inches aft of the heated leading
    • edge.
  45. Fuel Conditions

    Maximum asymmetric fuel differential for normal operations*...............................?

    Minimum Single Point refueling pressure is _____PSI and maximum is ____PSI. The maximum Single Point defueling pressure is ______PSI.

    *A lateral fuel imbalance of _______ has been demonstrated for emergency return.
    Fuel Conditions

    Maximum asymmetric fuel differential for normal operations*..............................400 lbs

    Minimum Single Point refueling pressure is 10 PSI and maximum is 55 PSI. The maximum Single Point defueling pressure is -10 PSI.

    *A lateral fuel imbalance of 800 lbs has been demonstrated for emergency return.
  46. Speed Limitations

    Max. Operating Mach (MMO), above 29,833 ft........? (indicated)
    Max Operating Knots (VMO), 8000 ft to 29.833 ft........?
    Max. Operating Knots (VMO), below 8000ft.................?
    Max Flap Extended Speed, Vfe Partial Flaps, 7 degree position...........?
    Max Flap Extended Speed, Vfe Partial Flaps, 15 degree position............?
    Max Flap Extended Speed, Vfe Partial Flaps, 35 degree position............?
    Speed Limitations

    • Max. Operating Mach (MMO), above 29,833 ft.........0.80 Mach (indicated)
    • Max Operating Knots (VMO), 8000 ft to 29.833 ft........305 KIAS
    • Max. Operating Knots (VMO), below 8000ft.................270 KIAS
    • Max Flap Extended Speed, Vfe Partial Flaps, 7 degree position...........250 KIAS
    • Max Flap Extended Speed, Vfe Partial Flaps, 15 degree position............200 KIAS
    • Max Flap Extended Speed, Vfe Partial Flaps, 35 degree position............175 KIAS
  47. Speed Limitations

    Max. Landing Gear Operating/Extended Speed, Vle/Vlo..................?
    Max Turbulent Air Penetration Speed........................?
    Max Speed Brake Extension Speed....................?
    Min Speed Brake Extension Speed......................?
    Min Single Engine Enroute Climb Speed..................?
    Max. Tire Ground Speed............................?
    Min Speed For Sustained Flight in Icing Conditions..........................?
    Speed Limitations

    • Max. Landing Gear Operating/Extended Speed, Vle/Vlo..................210 KIAS
    • Max Turbulent Air Penetration Speed........................225 KIAS/0.80 Mach
    • Max Speed Brake Extension Speed..................No Limit
    • Min Speed Brake Extension Speed......................Vref + 15 KIAS
    • Min Single Engine Enroute Climb Speed..............180 KIAS
    • Max. Tire Ground Speed.........................165
    • Min Speed For Sustained Flight in Icing Conditions.......................180 KIAS
  48. Takeoff and Landing Operational Limitations

    Maximum Altitude Limit........................?
    Maximum Tailwind Component...................?
    Maximum Demonstrated Crosswind Component (not Limiting; with of without thrust reversers)...................?
    The _________and _________ must be disengaged for takeof and landing.
    Takeoff and Landing Operational Limitations

    • Maximum Altitude Limit......................14,000 ft
    • Maximum Tailwind Component.................10 Knots
    • Maximum Demonstrated Crosswind Component (not Limiting; with of without thrust reversers)..................25 Knots
    • The autopilot and yaw damper must be disengaged for takeoff and landing.
  49. Takeoff and Landing
    Operational Limitations

    The lavatory doors must be ______ for taxi, takeoff, and landing.
    Takeoff and Landings are limited to ______ runway surfaces.
    Antiskid must be operational for _________.
    Except where required by AFM procedures, speed brakes,must be stowed prior to _______ for landing.
    • Takeoff and Landing
    • Operational Limitations

    • The lavatory doors must be latched open for taxi, takeoff, and landing.
    • Takeoff and Landings are limited to paved runway surfaces.
    • Antiskid must be operational for takeoff.
    • Except where required by AFM procedures, speed brakes,must be stowed prior to 500ft AGL for landing.
  50. Takeoff and Landing
    Operational Limitations

    Takeoff is prohibited with the following forms of contamination:
    With frost adhering to the following critical areas....
    -________
    -________
    -________
    • Takeoff and Landing
    • Operational Limitations

    • Takeoff is prohibited with the following forms of contamination:
    • With frost adhering to the following critical areas....
    • -Wing Leading Edge
    • -Upper Wing Surface
    • -Windshield
  51. Takeoff and Landing
    Operational Limitations

    Takeoff is prohibited with the following forms of contamination:
    With ice, snow, or slush adhering to the following critical areas....

    -______ -_______ -________
    -______ -_______ -________
    -______ -_______ -________
    -______ -_______
    • Takeoff and Landing
    • Operational Limitations

    • Takeoff is prohibited with the following forms of contamination:
    • With ice, snow, or slush adhering to the following critical areas....

    • -Wing leading edge and upper wing surface
    • -Flight control surfaces including all hinge gaps
    • -Horizontal stabilizer
    • -Vertical stabilizer
    • -Engine inlets
    • -Top of engine pylons
    • -Top of fuselage
    • -Windshield
    • -All static ports
    • -Angle of Attack Vanes
    • -Upper Surface of nose forward of the windshield
  52. Enroute Operational Limitations

    Maximum Operating Altitude..............?
    Maximum Altitude with Flaps Extended...............?
    Enroute Operational Limitations

    • Maximum Operating Altitude.............47,000ft
    • Maximum Altitude with Flaps Extended........18,000ft
  53. Cabin Pressurization Limitations

    Normal Cabin Pressurization Limitations.............?
    Pressure Relief Valve.........................................?
    Pressure Gauge Redline.....................................?
    Cabin Pressurization Limitations

    • Normal Cabin Pressurization Limitations...........0.0 to 9.3 (+- 0.1) PSID
    • Pressure Relief Valve.......................................9.6 (+- 0.1) PSID
    • Pressure Gauge Redline...................................9.7 PSID
  54. Maneuver Limitations

    Acrobatic maneuvers, including spins, are ______.
    Intentional stalls are prohibited above _____. Intentional full stalls are limited to idle thrust only.
    Maneuver Limitations

    • Acrobatic maneuvers, including spins, are prohibited.
    • Intentional stalls are prohibited above FL250. Intentional full stalls are limited to idle thrust only.
  55. Passenger and Baggage Compartments

    The maximum number of occupants in the passenger compartment is ______.
    The baggage compartment ________ and ______ systmes must be operational if baggage is to be carried in the compartment.
    The maximum floor loading distribution is ____ lbs per square foot.
    Passenger and Baggage Compartments

    • The maximum number of occupants in the passenger compartment is 12.
    • The baggage compartment smoke detection and extinguishing systmes must be operational if baggage is to be carried in the compartment.
    • The maximum floor loading distribution is 150 lbs per square foot.
  56. Supplemental Oxygen System

    Service the oxygen system with __________(MIL-O-27210).
    The use of medical oxygen is _______.

    Crew and passenger oxygen masks are not approved for use above ______ feet cabin altitude. Prolonged use of passenger masks above _____ feet cabin altitude is not recommended.

    The pressure-demand crew oxygen masks must be _______ to qualify as a quick donning oxygen mask.
    Supplemental Oxygen System

    • Service the oxygen system with Aviator's Breathing Oxygen (MIL-O-27210).
    • The use of medical oxygen is prohibited.

    Crew and passenger oxygen masks are not approved for use above 40,000 feet cabin altitude. Prolonged use of passenger masks above 25,000 feet cabin altitude is not recommended.

    The pressure-demand crew oxygen masks must be properly stowed in their containers to qualify as a quick donning oxygen mask.
  57. Thrust Reversers

    A satisfactory preflight check of the thrust reversersmust be accomplished in accordance with Section III, Normal Procedures on _______ and on any flight that is predicated on the use of the thrust reversers for perfomance or the first flight ______ on the airplane.
    Reverse thrust power must be reduced to the idle reverse detent position at ______ KIAS on landing roll.
    Takeoff performance data must not be predicated on the use of the thrust reversers when the ground operating temperature is below_____.
    Thrust Reversers

    • A satisfactory preflight check of the thrust reversers must be accomplished in accordance with Section III, Normal Procedures on the first flight of the day and on any flight that is predicated on the use of the thrust
    • reversers for perfomance or the first flight after any maintenance action has been performed on the airplane.
    • Reverse thrust power must be reduced to the idle reverse detent position at 65 KIAS on landing roll.
    • Takeoff performance data must not be predicated on the use of the thrust
    • reversers when the ground operating temperature is below -40 C.
  58. Thrust Reversers

    Deployment of the trhust reversers for more than _____ seconds with the APU operating is prohibited.
    Static-ground operation of the engines is limited to _____ if the thrust reversers are deployed.
    The use of thrust reversers is prohibited during ______.
    The use of thrust reversers to ______ is prohibited.
    Thrust Reversers

    • Deployment of the trhust reversers for more than 30 seconds with the APU operating is prohibited.
    • Static-ground operation of the engines is limited to idle power if the thrust reversers are deployed.
    • The use of thrust reversers is prohibited during touch-and-go landings.
    • The use of thrust reversers to back the airplane is prohibited.
  59. Honeywell Primus Epic System

    The Honeywell PRIMUS EPIC for the Cessna Citation SOVEREIGN Pilot's Guides, part numbers A28-1146-168 and A28-1146-183, Revision 1, or later applicable revision, must be ______ to the flight crew.
    Dispatch is prohibited when any of the following CAS messages are displayed: __________.
    Dispatch is prohibited following a flight where either a DU 1-2-3-4- O'TEMP or MAU 1-2-3-4 O'TEMP CAS Message was displayed, until O'TEMP or MAU 1-2-3-4 O'TEMP CAS Message was displayed, until _________.
    Honeywell Primus Epic System

    • The Honeywell PRIMUS EPIC for the Cessna Citation SOVEREIGN Pilot's Guides, part numbers A28-1146-168 and A28-1146-183, Revision 1, or later applicable revision, must be immediately available to the flight crew.
    • Dispatch is prohibited when any of the following CAS messages are displayed: DU 1-2-3-4 O'TEMP or MAU 1-2-3-4 O'TEMP.
    • Dispatch is prohibited following a flight where either a DU 1-2-3-4-
    • O'TEMP or MAU 1-2-3-4 O'TEMP CAS Message was displayed, until O'TEMP or
    • MAU 1-2-3-4 O'TEMP CAS Message was displayed, until the condition is identified and corrected.
  60. Honeywell Primus Epic System

    All display units must be ____________.
    Dispatch with a DU in _______________ is prohibited.
    Reversion of both PFDs to ___________ is prohibited.
    Taxiing the airplane is prohibited until the AHRS _____ is completed.
    Honeywell Primus Epic System

    • All display units must be installed and operational.
    • Dispatch with a DU in reversionary mode is prohibited.
    • Reversion of both PFDs to DU2 or DU3 is prohibited.
    • Taxiing the airplane is prohibited until the AHRS ground alignment is completed.
  61. Autopilot

    One pilot must remain seated, with the seatbelt fastened, during ________.
    Autopilot operation is prohibited if any of the following is true:

    -________________
    -________________
    -________________
    Autopilot

    • One pilot must remain seated, with the seatbelt fastened, during all autopilot operations.
    • Autopilot operation is prohibited if any of the following is true:

    • -Any comparison monitor annunciation is activated.
    • -Either PFD is in ATT or HDG reversion.
    • -Either AHRS is failed.
  62. Autopilot

    Autopilot Minimum-Use-Height:
    -Enroute, and Descent ______ feet AGL.
    -Precision Approach (Category I and II ILS) _____ feet AGL.
    -Nonprecision Approach ______ feet AGL.
    -Takeoff, Climb, and Missed Approach _____ feet AGL.
    Autopilot

    • Autopilot Minimum-Use-Height:
    • -Enroute, and Descent 1,000 feet AGL.
    • -Precision Approach (Category I and II ILS) 80 feet AGL.
    • -Nonprecision Approach 200 feet AGL.
    • -Takeoff, Climb, and Missed Approach 400 feet AGL.
  63. Autopilot

    Autopilot operation is prohibited during in-flight engine starts using ________.
    Configuring the aircraft displays to _______ fuel and weight units is prohibited.
    When the Flight Director or Autopilot is coupled to VOR or ILS, ________ mode must be selected (HDG bug synced to current heading) prior to switching navigation frequencies. When the next VOR or ILS frequency is satisfactorily received, ______ mode may be reengaged.
    Autopilot

    • Autopilot operation is prohibited during in-flight engine starts using starter assist.
    • Configuring the aircraft displays to metric fuel and weight units is prohibited.
    • When the Flight Director or Autopilot is coupled to VOR or ILS, HDG mode must be selected (HDG bug synced to current heading) prior to switching navigation frequencies. When the next VOR or ILS frequency issatisfactorily received, NAV mode may be reengaged.
  64. Autopilot

    For airplanes 680-0001 thru -0290 not incorporating SB680-34-20 (Epic Phase 5 Software Upgrade), the use of ______ mode to ______ transition from LNAV to VOR or ILS approach is prohibited.
    HF radio transmissions are prohibited when navigation is predicated on the use of the ________.
    Autopilot

    • For airplanes 680-0001 thru -0290 not incorporating SB680-34-20 (Epic Phase 5 Software Upgrade), the use of Preview mode to auto transition from LNAV to VOR or ILS approach is prohibited.
    • HF radio transmissions are prohibited when navigation is predicated on the use of the Automatic Direction Finder (ADF)
    • .
  65. Standby Flight Display

    The standby flight disply (including ATT, ALT and ASI) and standby HSI must be ___________.
    Standby Flight Display

    The standby flight disply (including ATT, ALT and ASI) and standby HSI must be functioning prior to takeoff.
  66. Avionics

    When displayed, the geographic-referenced airplane symbol on the optional electronic charts _______ be used for navigation.
    Operators with the optional electronic charts must have __________ available to the flight crew.
    The Data Start Date currency __________ on the REVISION INFO window prior to use.
    The flight crew is responsible for _________ of charts for the planned flight.
    Avionics

    • When displayed, the geographic-referenced airplane symbol on the optional electronic charts must not be used for navigation.
    • Operators with the optional electronic charts must have back-up charts available to the flight crew.
    • The Data Start Date currency must be verified on the REVISION INFO window prior to use.
    • The flight crew is responsible for verifying availability of charts for the planned flight.
  67. Ice and Rain Protection

    CAUTION

    Do not operate the aircraft above ______ with wing anti-ice selected on.
    Ice and Rain Protection

    CAUTION

    Do not operate the aircraft above FL410 with wing anti-ice selected on.

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